EP2199544B1 - Assembly of guide vanes - Google Patents

Assembly of guide vanes Download PDF

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Publication number
EP2199544B1
EP2199544B1 EP08172599.6A EP08172599A EP2199544B1 EP 2199544 B1 EP2199544 B1 EP 2199544B1 EP 08172599 A EP08172599 A EP 08172599A EP 2199544 B1 EP2199544 B1 EP 2199544B1
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EP
European Patent Office
Prior art keywords
turbine engine
guide vane
engine according
outer collar
vane stage
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EP08172599.6A
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German (de)
French (fr)
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EP2199544A1 (en
Inventor
Rodolphe Lebrun
Alain Derclaye
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Safran Aero Boosters SA
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Techspace Aero SA
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Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP08172599.6A priority Critical patent/EP2199544B1/en
Priority to CA2686988A priority patent/CA2686988C/en
Priority to US12/640,062 priority patent/US8469662B2/en
Publication of EP2199544A1 publication Critical patent/EP2199544A1/en
Application granted granted Critical
Publication of EP2199544B1 publication Critical patent/EP2199544B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the present invention relates to turbomachine stators. It relates more particularly to a rectifier architecture in an axial compressor of a turbomachine.
  • Axial compressors are well known per se and are used in several types of applications. In particular, they are used in turbojet engines.
  • These low or high pressure compressors comprise several stages of rotating blades which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the next stage.
  • rectifier stages consist essentially of fixed vanes connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein.
  • the contacts between the platform of the blade and the outer shell may be of planar-curve, curve-curve or plane-plane respectively.
  • planar-curve or curve-curve assemblies do not marry perfectly.
  • plane-curve type contact it can be easily understood that the two surfaces do not marry perfectly.
  • curve-curve type contact the manufacturing tolerances are such that the two surfaces do not have exactly the same radius of curvature and, therefore, do not fit perfectly one of the other.
  • a plane-plane type contact where the two surfaces fit perfectly with each other makes it possible to reduce the stresses induced during assembly and to avoid instability of the positioning of the blade around the point of attachment. .
  • Requirement EP 1 801 357 A1 has a turbomachine stator vane comprising a ring of fixed vanes, mounted on an outer shell, each blade comprising a platform intended to be fixed to the outer shell.
  • Blading is characterized in that the outer shell comprises a plurality of individual housings for the platforms, machined in the thickness of the ferrule, the shape of each housing being complementary to that of the corresponding platform.
  • the housings are in the form of flat-bottomed recesses and the platforms are in the form of a plate.
  • the patent US 6,543,995 B1 has a rectifier where the contact between the platform of the blade and the outer shell is of plan-plane type.
  • Flat facets are machined on the outer shell and disposed circumferentially on the side opposite to the aerodynamic stream, and the blade platforms have a flat surface on their inner side (on the blade side).
  • the contact between the platform of the blade and the outer shell is on the opposite side to the aerodynamic vein.
  • Such an assembly architecture requires machining a series of large openings in the outer shell to allow the passage of the blade through it.
  • the disclosed rectifier architecture requires the use of an elastomeric material to fill the interstices between the blade profile and the openings in the outer shell; this in order to obtain a perfectly smooth surface on the side of the aerodynamic vein.
  • the present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.
  • the present invention more specifically aims to provide an outer dawn-ferrule assembly architecture where the assembly constraints are reduced.
  • Another object of the present invention is to provide an exterior dawn-ferrule assembly architecture where the only openings in the outer shell are those required by the fastening systems (rivets, bolts, "lockbolt”, etc.).
  • the present invention also aims to provide an outer dawn-ferrule assembly architecture where the platforms are arranged to improve aerodynamic performance.
  • the present invention discloses a turbomachine rectifying stage comprising a set of fixed vanes connecting an inner ferrule to an outer ferrule, said fixed vanes having attachment platforms having flat surfaces cooperating with a plurality of juxtaposed plane facets, said facets planes located on the inner face of the outer shell to ensure a fixing with a contact plane / plane between the vanes and the outer ring, characterized in that said platforms are arranged contiguously so as to provide a continuous, smooth surface to the airflow.
  • the present invention also discloses a method of manufacturing a turbomachine rectifier stage according to claim 3 comprising a resin transfer molding step of the outer shell or a co-molding step ("cocuring") by transfer of resin for the assembly of the outer shell to the blades.
  • the present invention relates to an architecture for assembling the stator vanes to the outer ferrule in a turbocharger.
  • the figure 1 shows a section of a part of a turbocharger where one can see the rotating blades 3 driven by the compressor shaft and the stator vanes 2 attached to the inner ring 4 and outer 5.
  • the outer shell instead of being a continuous curved surface, consists of a plurality of plane facets disposed on the side of the aerodynamic stream; the plane facets being juxtaposed.
  • the outer shell is formed of a plurality of plane facets on the side of the aerodynamic vein and the opposite side to the aerodynamic stream.
  • an outer shell consisting of a plurality of flat segments, the latter being also juxtaposed.
  • the outer shell is made of composite material and obtained by a Resin Transfer Molding (RTM) technique.
  • RTM Resin Transfer Molding
  • the blades comprise a platform having a flat surface on the opposite side to the blade of the blade.
  • the contact between the platform of the blade and the plane facets or plane segments of the outer shell is made exclusively on the side of the aerodynamic vein.
  • the figure 3 illustrates the plane-plane type contact between the platform 7 of the blade 2 and the planar segments 10 of the outer shell on the inner face of the outer shell.
  • the platforms 7 are arranged side by side to provide a smooth continuous surface to the flow of air which improves the aerodynamic performance compared to a welded configuration where the weld bead opens into the vein.
  • the only openings required in the outer shell are those for the attachment systems of the platform of the blade to the inner face of the outer shell.
  • the fastening system is a bolted fastener 11 (see FIG. Figures 4 and 5 ). Bolting takes place at the plane facets or flat segments of the outer shell or at the flanges provided for the assembly of ferrules together.
  • the figure 4 presents the first configuration.
  • a threaded rod integral with the blade passes through the ferrule and is bolted to the outer shell by a nut on the opposite side to the aerodynamic vein.
  • an L-shaped flange 8 is integral with the platform of the blade and bolted by connection with the assembly flange 1 of the outer rings 5 (see also FIG. figure 1 ).
  • a "lockbolt” 9 further maintains the platform of the blade in contact with the facet or segment plane of the outer shell.
  • the platforms of the blades are assembled to the facets or flat segments of the outer shell only by means of "lockbolts".
  • each platform is fixed to the plane segment 10 of the outer shell by means of two "lockbolts" 9.
  • the platforms are fixed by means of rivets (not shown).
  • the vanes can be secured by means of fastening systems that combine bolted fasteners, rivets and "lockbolts".
  • the invention has the advantage that only one or two fasteners, namely the bolted fastener, the rivet or the "lockbolt", are required to attach a blade platform to a flat facet or segment. plan of the outer shell.
  • the platforms are glued to the outer shell or the platform of the blade is assembled to the outer shell by co-molding ("cocuring" in English).
  • co-molding in English.
  • the latter assembly technique is based on the RTM process and consists in simultaneously making the composite parts (blade and outer shell) and the junction between the two parts.
  • the plane-plane contact allows a reduction of assembly constraints.
  • plane facets or planar segments are directly molded to finished dimensions, which greatly reduces machining operations relative to to the state-of-the-art manufacturing ranges US 6, 543, 995 B1 where the plane facets or flat segments are milled out of a part roughed by turning and where it is necessary to mill the openings and drillings.
  • junction lines between blade platforms are not parallel to the velocity vector of the air flow, the latter being biased relative to the junction lines. This has the advantage of restricting the creepage distances with respect to a configuration where the velocity vector of the air flow is parallel to the connecting lines, as is the case in the state of the art. US 6, 543, 995 B1 , and therefore minimize aerodynamic disturbances.
  • the only openings required in the outer shell are those for the mounting holes.
  • the outer shell is free of any opening.
  • the removal of large openings in the outer shell has the advantage of not reducing the structural strength of the shell. This is particularly advantageous for long fiber composite ferrules where the openings in the ferrule sever the fibers and therefore particularly reduce the mechanical strength of the material.
  • the blade assembly is perfectly interchangeable, that is to say that the platform and the fastening system can be identical while having blade profiles or materials. different.

Description

Objet de l'inventionObject of the invention

La présente invention se rapporte à des stators de turbomachines. Elle se rapporte plus particulièrement à une architecture de redresseur dans un compresseur axial d'une turbomachine.The present invention relates to turbomachine stators. It relates more particularly to a rectifier architecture in an axial compressor of a turbomachine.

Etat de la techniqueState of the art

Les compresseurs axiaux sont bien connus en soi et sont utilisés dans plusieurs types d'applications. En particulier, ils sont utilisés dans les turboréacteurs.Axial compressors are well known per se and are used in several types of applications. In particular, they are used in turbojet engines.

Ces compresseurs basse ou haute pression comportent plusieurs étages d'aubes tournantes qui sont séparés par des étages redresseurs qui ont pour but de repositionner le vecteur vitesse du fluide sortant de l'étage précédent avant de l'envoyer vers l'étage suivant.These low or high pressure compressors comprise several stages of rotating blades which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the next stage.

Ces étages redresseurs sont constitués essentiellement d'aubes fixes reliant une virole extérieure à une virole intérieure, toutes deux concentriques et délimitant la zone d'écoulement d'air ou veine aérodynamique.These rectifier stages consist essentially of fixed vanes connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein.

Deux grands types d'architecture d'assemblage des aubes fixes à la virole extérieure existent. D'une part, l'architecture où la plate-forme de l'aube est rivetée à la virole extérieure du côté opposé à la veine aérodynamique; une telle architecture est illustrée à la figure 3 du brevet US 6,543,995 B1 . D'autre part, l'architecture où la plate-forme de l'aube est fixée à la virole extérieure du côté de la veine aérodynamique. Dans ce dernier cas, la plate-forme est soit attachée par un système d'encoches, soit soudée ou boulonnée comme illustré à la figure 2, soit encore rivetée. Des exemples de telles réalisations sont visibles respectivement dans les documents US 5,584,654 A , US 5,474,419 A , EP 1 936 121 A1 et EP 0 953 729 B1 .There are two main types of fixed-blade assembly architecture at the outer shell. On the one hand, the architecture where the platform of the dawn is riveted to the outer shell on the opposite side to the aerodynamic vein; such an architecture is illustrated in the figure 3 patent US 6,543,995 B1 . On the other hand, the architecture where the platform of the dawn is attached to the outer shell on the side of the aerodynamic vein. In the latter case, the platform is either attached by a notch system, either welded or bolted as shown in figure 2 , still riveted. Examples of such achievements are shown respectively in the documents US 5,584,654 A , US 5,474,419 A , EP 1 936 121 A1 and EP 0 953 729 B1 .

Sauf dans le cas où les aubes sont soudées à la virole extérieure, les contacts entre la plate-forme de l'aube et la virole extérieure peuvent être respectivement de type plan-courbe, courbe-courbe ou plan-plan.Except in the case where the vanes are welded to the outer shell, the contacts between the platform of the blade and the outer shell may be of planar-curve, curve-curve or plane-plane respectively.

L'inconvénient des assemblages de type plan-courbe ou courbe-courbe est que les deux surfaces en contact ne s'épousent pas parfaitement. Dans le cas d'un contact de type plan-courbe, on peut aisément comprendre que les deux surfaces ne s'épousent pas parfaitement. Dans le cas d'un contact de type courbe-courbe, les tolérances de fabrication sont telles que les deux surfaces n'ont pas exactement le même rayon de courbure et, par conséquent, ne s'accommodent pas parfaitement l'une de l'autre.The disadvantage of the planar-curve or curve-curve assemblies is that the two surfaces in contact do not marry perfectly. In the case of a plane-curve type contact, it can be easily understood that the two surfaces do not marry perfectly. In the case of a curve-curve type contact, the manufacturing tolerances are such that the two surfaces do not have exactly the same radius of curvature and, therefore, do not fit perfectly one of the other.

S'il n'y a pas une bonne jonction entre les deux surfaces autour du point de fixation, cela peut induire en cas de vibrations une usure prématurée entre les deux surfaces, appelée « fretting ». Pour éviter ce phénomène, il est nécessaire d'appliquer une précontrainte lors de la fixation de la plate-forme d'aube à la virole.If there is not a good junction between the two surfaces around the point of attachment, it can induce in the event of vibrations premature wear between the two surfaces, called "fretting". To avoid this phenomenon, it is necessary to apply prestressing when attaching the blade platform to the shell.

Un contact de type plan-plan où les deux surfaces s'accommodent parfaitement l'une de l'autre permet de réduire les contraintes induites lors de l'assemblage et d'éviter une instabilité du positionnement de l'aube autour du point de fixation.A plane-plane type contact where the two surfaces fit perfectly with each other makes it possible to reduce the stresses induced during assembly and to avoid instability of the positioning of the blade around the point of attachment. .

La demande EP 1 801 357 A1 présente un aubage statorique de turbomachine comportant une couronne d'aubes fixes, montées sur une virole extérieure, chaque aube comportant une plate-forme destinée à être fixée à la virole extérieure. L'aubage est caractérisé par le fait que la virole extérieure comporte une pluralité de logements individuels pour les plate-formes, usinés dans l'épaisseur de la virole, la forme de chaque logement étant complémentaire de celle de la plate-forme correspondante. Selon une forme de réalisation préférée, les logements se présentent sous forme d'évidements à fonds plats et les plate-formes se présentent sous la forme de plaque.Requirement EP 1 801 357 A1 has a turbomachine stator vane comprising a ring of fixed vanes, mounted on an outer shell, each blade comprising a platform intended to be fixed to the outer shell. Blading is characterized in that the outer shell comprises a plurality of individual housings for the platforms, machined in the thickness of the ferrule, the shape of each housing being complementary to that of the corresponding platform. According to a preferred embodiment, the housings are in the form of flat-bottomed recesses and the platforms are in the form of a plate.

Le brevet US 6,543,995 B1 présente un redresseur où le contact entre la plate-forme de l'aube et la virole extérieure est de type plan-plan. Des facettes planes sont usinées sur la virole extérieure et disposées de manière circonférentielle du côté opposé à la veine aérodynamique, et les plate-formes des aubes présentent une surface plane sur leur face intérieure (du côté de la pale). Le contact entre la plate-forme de l'aube et la virole extérieure s'effectue du côté opposé à la veine aérodynamique. Une telle architecture d'assemblage nécessite d'usiner une série de larges ouvertures dans la virole extérieure afin de permettre le passage de l'aube à travers cette dernière.The patent US 6,543,995 B1 has a rectifier where the contact between the platform of the blade and the outer shell is of plan-plane type. Flat facets are machined on the outer shell and disposed circumferentially on the side opposite to the aerodynamic stream, and the blade platforms have a flat surface on their inner side (on the blade side). The contact between the platform of the blade and the outer shell is on the opposite side to the aerodynamic vein. Such an assembly architecture requires machining a series of large openings in the outer shell to allow the passage of the blade through it.

Ces larges ouvertures ont pour inconvénient de fragiliser le matériau constituant la virole extérieure. De plus, l'architecture de redresseur divulguée nécessite l'utilisation d'un matériau élastomère pour combler les interstices entre le profil de l'aube et les ouvertures dans la virole extérieure; ceci afin d'obtenir une surface parfaitement lisse du côté de la veine aérodynamique.These large openings have the disadvantage of weakening the material constituting the outer shell. In addition, the disclosed rectifier architecture requires the use of an elastomeric material to fill the interstices between the blade profile and the openings in the outer shell; this in order to obtain a perfectly smooth surface on the side of the aerodynamic vein.

Buts de l'inventionGoals of the invention

La présente invention vise à fournir une solution qui permette de s'affranchir des inconvénients de l'état de la technique.The present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.

La présente invention vise plus particulièrement à fournir une architecture d'assemblage aube-virole extérieure où les contraintes d'assemblage sont réduites.The present invention more specifically aims to provide an outer dawn-ferrule assembly architecture where the assembly constraints are reduced.

La présente invention a également pour but de fournir une architecture d'assemblage aube-virole extérieure où les seules ouvertures dans la virole extérieure sont celles requises par les systèmes de fixation (rivets, boulons, "lockbolt"...) .Another object of the present invention is to provide an exterior dawn-ferrule assembly architecture where the only openings in the outer shell are those required by the fastening systems (rivets, bolts, "lockbolt", etc.).

La présente invention vise également à fournir une architecture d'assemblage aube-virole extérieure où les plate-formes sont disposées de manière à améliorer les performances aérodynamiques.The present invention also aims to provide an outer dawn-ferrule assembly architecture where the platforms are arranged to improve aerodynamic performance.

Principaux éléments caractéristiques de Main features of l'inventionthe invention

La présente invention divulgue un étage redresseur de turbomachine comportant un ensemble d'aubes fixes reliant une virole intérieure à une virole extérieure, lesdites aubes fixes comportant des plate-formes de fixation présentant des surfaces planes coopérant avec une pluralité de facettes planes juxtaposées, lesdites facettes planes se trouvant sur la face interne de la virole extérieure afin d'assurer une fixation avec un contact de type plan/plan entre les aubes fixes et la virole extérieure, caractérisé en ce que lesdites plate-formes sont disposées de manière jointive afin d'offrir une surface continue sans aspérité au flux d'air.The present invention discloses a turbomachine rectifying stage comprising a set of fixed vanes connecting an inner ferrule to an outer ferrule, said fixed vanes having attachment platforms having flat surfaces cooperating with a plurality of juxtaposed plane facets, said facets planes located on the inner face of the outer shell to ensure a fixing with a contact plane / plane between the vanes and the outer ring, characterized in that said platforms are arranged contiguously so as to provide a continuous, smooth surface to the airflow.

Selon des modes particuliers de l'invention, l'étage redresseur comporte au moins une ou une combinaison appropriée des caractéristiques suivantes :

  • la virole extérieure est formée par une pluralité de segments plans juxtaposés.
  • la virole extérieure est réalisée en matériau composite.
  • les seules ouvertures dans la virole extérieure sont celles requises pour les systèmes de fixation des plate-formes des aubes à la face interne de la virole extérieure.
  • les systèmes de fixation comportent une attache boulonnée.
  • l'attache boulonnée comporte une tige filetée solidaire de l'aube, ladite tige traversant la virole extérieure pour être boulonnée sur la face externe de la virole extérieure par un écrou.
  • l'attache boulonnée comprend une bride en L intégrée à la plate-forme de l'aube et ladite bride est boulonnée à une bride d'assemblage des viroles extérieures.
  • les systèmes de fixation comprennent des rivets ou des "lockbolts".
  • les plate-formes des aubes sont collées aux facettes planes ou segments plans de la virole extérieure réalisée en matériau composite.
  • les systèmes de fixation sont une combinaison de rivets, d'attaches boulonnées et de "lockbolts".
According to particular embodiments of the invention, the rectifier stage comprises at least one or a suitable combination of the following characteristics:
  • the outer shell is formed by a plurality of juxtaposed planar segments.
  • the outer shell is made of composite material.
  • the only openings in the outer shell are those required for the fastening systems of the blade platforms to the inner face of the outer shell.
  • the fastening systems include a bolted fastener.
  • the bolted fastener comprises a threaded rod integral with the blade, said rod passing through the outer shell to be bolted to the outer face of the outer shell by a nut.
  • the bolted fastener comprises an integral L-shaped flange at the blade platform and said flange is bolted to an assembly flange of the outer ferrules.
  • fastening systems include rivets or "lockbolts".
  • the platforms of the blades are glued to the plane facets or flat segments of the outer shell made of composite material.
  • fastening systems are a combination of rivets, bolted fasteners and lockbolts.

La présente invention divulgue également un procédé de fabrication d'un étage redresseur de turbomachine selon la revendication 3 comportant une étape de moulage par transfert de résine de la virole extérieure ou une étape de co-moulage ("cocuring") par transfert de résine pour l'assemblage de la virole extérieure aux aubes fixes.The present invention also discloses a method of manufacturing a turbomachine rectifier stage according to claim 3 comprising a resin transfer molding step of the outer shell or a co-molding step ("cocuring") by transfer of resin for the assembly of the outer shell to the blades.

Brève description des figuresBrief description of the figures

  • La figure 1 représente une coupe d'une partie d'un turbocompresseur.The figure 1 represents a section of a part of a turbocharger.
  • La figure 2 représente une vue tridimensionnelle de deux types d'assemblage aube-virole extérieure selon l'état de la technique.The figure 2 represents a three-dimensional view of two types of exterior dawn-ferrule assembly according to the state of the art.
  • La figure 3 représente deux vues tridimensionnelles d'un contact entre une plate-forme d'aube et une virole extérieure selon l'invention.The figure 3 represents two three-dimensional views of a contact between a blade platform and an outer shell according to the invention.
  • La figure 4 représente une vue tridimensionnelle du boulonnage de la plate-forme d'aube à la virole extérieure selon l'invention.The figure 4 represents a three-dimensional view of the bolting of the blade platform to the outer shell according to the invention.
  • La figure 5 représente une vue tridimensionnelle du boulonnage de la plate-forme d'aube à la virole extérieure selon une autre configuration de l'invention.The figure 5 represents a three-dimensional view of the bolting of the blade platform to the outer shell according to another embodiment of the invention.
  • La figure 6 représente une vue tridimensionnelle des plate-formes d'aubes fixées à la virole extérieure au moyen de "lockbolts" selon l'invention.The figure 6 represents a three-dimensional view of the blade platforms fixed to the outer shell by means of "lockbolts" according to the invention.
Légende :Legend:

  1. (1) Bride d'assemblage entre viroles extérieures(1) Mounting flange between outer ferrules
  2. (2) Aubes fixes(2) Fixed dances
  3. (3) Aubes mobiles(3) Moving temples
  4. (4) Virole intérieure(4) Inner ferrule
  5. (5) Virole extérieure(5) outer shell
  6. (6) Abradable(6) Abradable
  7. (7) Plateforme(7) Platform
  8. (8) Plateforme avec bride intégrée(8) Platform with integrated flange
  9. (9) "Lockbolt"(9) "Lockbolt"
  10. (10) Segment plan de la virole extérieure(10) Planar segment of the outer shell
  11. (11) Attache boulonnée(11) Bolted fastener
Description détaillée de l'inventionDetailed description of the invention

La présente invention concerne une architecture d'assemblage des aubes de redresseur à la virole extérieure dans un turbocompresseur.The present invention relates to an architecture for assembling the stator vanes to the outer ferrule in a turbocharger.

La figure 1 montre une coupe d'une partie d'un turbocompresseur où on peut y voir les aubes rotatives 3 entrainées par l'arbre du compresseur et les aubes de redresseur 2 fixées aux viroles intérieure 4 et extérieure 5.The figure 1 shows a section of a part of a turbocharger where one can see the rotating blades 3 driven by the compressor shaft and the stator vanes 2 attached to the inner ring 4 and outer 5.

Dans la présente invention, la virole extérieure, au lieu d'être une surface courbe continue, est constituée d'une pluralité de facettes planes disposées du côté de la veine aérodynamique; les facettes planes étant juxtaposées.In the present invention, the outer shell, instead of being a continuous curved surface, consists of a plurality of plane facets disposed on the side of the aerodynamic stream; the plane facets being juxtaposed.

Selon une variante de réalisation de l'invention, la virole extérieure est formée d'une pluralité de facettes planes du côté de la veine aérodynamique et du côté opposé à la veine aérodynamique. Dans ce cas, on parlera d'une virole extérieure constituée d'une pluralité de segments plans, ces derniers étant également juxtaposés.According to an alternative embodiment of the invention, the outer shell is formed of a plurality of plane facets on the side of the aerodynamic vein and the opposite side to the aerodynamic stream. In this case, we will speak of an outer shell consisting of a plurality of flat segments, the latter being also juxtaposed.

Par la suite, on utilisera indifféremment face interne de la virole extérieure ou du côté de la veine aérodynamique. On utilisera également indifféremment face externe de la virole extérieure ou du côté opposé à la veine aérodynamique.Subsequently, it will be used indifferently inner face of the outer shell or the side of the aerodynamic vein. It will also be used indifferently outer face of the outer shell or the opposite side to the aerodynamic vein.

De préférence, la virole extérieure est en matériau composite et obtenue par une technique de moulage par transfert de résine (Resin Transfer Moulding - RTM).Preferably, the outer shell is made of composite material and obtained by a Resin Transfer Molding (RTM) technique.

Pour établir un contact de type plan-plan entre l'aube et les facettes planes ou segments plans de la virole extérieure, les aubes comportent une plate-forme présentant une surface plane du côté opposé à la pale de l'aube.To establish a plane-plane contact between the blade and the plane facets or plane segments of the outer shell, the blades comprise a platform having a flat surface on the opposite side to the blade of the blade.

Selon l'invention, le contact entre la plate-forme de l'aube et les facettes planes ou segments plans de la virole extérieure s'effectue exclusivement du côté de la veine aérodynamique.According to the invention, the contact between the platform of the blade and the plane facets or plane segments of the outer shell is made exclusively on the side of the aerodynamic vein.

La figure 3 illustre le contact de type plan-plan entre la plate-forme 7 de l'aube 2 et les segments plans 10 de la virole extérieure sur la face interne de la virole extérieure.The figure 3 illustrates the plane-plane type contact between the platform 7 of the blade 2 and the planar segments 10 of the outer shell on the inner face of the outer shell.

Les plate-formes 7 sont disposées côte à côte afin d'offrir une surface continue sans aspérité au flux d'air ce qui permet d'améliorer les performances aérodynamiques par rapport à une configuration soudée où le cordon de soudure débouche dans la veine.The platforms 7 are arranged side by side to provide a smooth continuous surface to the flow of air which improves the aerodynamic performance compared to a welded configuration where the weld bead opens into the vein.

Les seules ouvertures requises dans la virole extérieure sont celles pour les systèmes de fixation de la plate-forme de l'aube à la face interne de la virole extérieure.The only openings required in the outer shell are those for the attachment systems of the platform of the blade to the inner face of the outer shell.

Selon une forme particulière de réalisation de l'invention, le système de fixation est une attache boulonnée 11 (voir figures 4 et 5). Le boulonnage s'effectue au niveau des facettes planes ou segments plans de la virole extérieure ou au niveau des brides prévues pour l'assemblage des viroles entre elles.According to a particular embodiment of the invention, the fastening system is a bolted fastener 11 (see FIG. Figures 4 and 5 ). Bolting takes place at the plane facets or flat segments of the outer shell or at the flanges provided for the assembly of ferrules together.

La figure 4 présente la première configuration. Une tige filetée solidaire de l'aube traverse la virole et est boulonnée à la virole extérieure par un écrou du côté opposé à la veine aérodynamique.The figure 4 presents the first configuration. A threaded rod integral with the blade passes through the ferrule and is bolted to the outer shell by a nut on the opposite side to the aerodynamic vein.

Selon la seconde configuration de la figure 5, une bride 8 en L est solidaire de la plate-forme de l'aube et boulonnée par liaison avec la bride d'assemblage 1 des viroles extérieures 5 (voir également la figure 1). Un « lockbolt» 9 maintient en outre la plate-forme de l'aube en contact avec la facette ou segment plan de la virole extérieure.According to the second configuration of the figure 5 , an L-shaped flange 8 is integral with the platform of the blade and bolted by connection with the assembly flange 1 of the outer rings 5 (see also FIG. figure 1 ). A "lockbolt" 9 further maintains the platform of the blade in contact with the facet or segment plane of the outer shell.

Selon une autre forme de réalisation présentée à la figure 6, les plate-formes des aubes sont assemblées aux facettes ou segments plans de la virole extérieure uniquement au moyen de "lockbolts". Dans l'exemple illustré, chaque plate-forme est fixée au segment plan 10 de la virole extérieure au moyen de deux "lockbolts" 9.According to another embodiment presented to figure 6 , the platforms of the blades are assembled to the facets or flat segments of the outer shell only by means of "lockbolts". In the illustrated example, each platform is fixed to the plane segment 10 of the outer shell by means of two "lockbolts" 9.

En variante, les plate-formes sont fixées au moyen de rivets (non représenté).Alternatively, the platforms are fixed by means of rivets (not shown).

Selon d'autres formes de réalisation, les aubes peuvent être fixées au moyen de systèmes de fixation combinant attaches boulonnées, rivets et "lockbolts".In other embodiments, the vanes can be secured by means of fastening systems that combine bolted fasteners, rivets and "lockbolts".

L'invention présente l'avantage que seulement un ou deux éléments de fixation, à savoir l'attache boulonnée, le rivet ou le "lockbolt", sont requis pour fixer une plate-forme d'aube à une facette plane ou à un segment plan de la virole extérieure.The invention has the advantage that only one or two fasteners, namely the bolted fastener, the rivet or the "lockbolt", are required to attach a blade platform to a flat facet or segment. plan of the outer shell.

Selon une autre variante de réalisation de l'invention, les plate-formes sont collées à la virole extérieure ou encore la plate-forme de l'aube est assemblée à la virole extérieure par co-moulage ("cocuring" en anglais). Cette dernière technique d'assemblage est basée sur le procédé RTM et consiste à réaliser simultanément les pièces composites (aube et virole extérieure) et la jonction entre les deux pièces.According to another embodiment of the invention, the platforms are glued to the outer shell or the platform of the blade is assembled to the outer shell by co-molding ("cocuring" in English). The latter assembly technique is based on the RTM process and consists in simultaneously making the composite parts (blade and outer shell) and the junction between the two parts.

Avantages de l'architecture d'assemblage selon l'invention.Advantages of the assembly architecture according to the invention.

Le contact plan-plan permet une réduction des contraintes d'assemblage.The plane-plane contact allows a reduction of assembly constraints.

La réduction des contraintes statiques lors de l'assemblage permet l'utilisation de matériaux composites pour la virole extérieure et d'alliages légers ou composites pour les aubes et par conséquent, une réduction de la masse.The reduction of the static stresses during the assembly allows the use of composite materials for the outer shell and light or composite alloys for the blades and consequently a reduction of the mass.

Dans le cadre de la fabrication d'une virole extérieure en composite par la technique de moulage par transfert de résine (RTM), les facettes planes ou segments plans sont directement moulés à cotes finies, ce qui réduit fortement les opérations d'usinage par rapport aux gammes de fabrication de l'état de l'art US 6, 543, 995 B1 où les facettes planes ou segments plans sont fraisées hors d'une pièce ébauchée par tournage et où il faut fraiser les ajours et perçages.As part of the manufacture of a composite outer shell by the resin transfer molding (RTM) technique, plane facets or planar segments are directly molded to finished dimensions, which greatly reduces machining operations relative to to the state-of-the-art manufacturing ranges US 6, 543, 995 B1 where the plane facets or flat segments are milled out of a part roughed by turning and where it is necessary to mill the openings and drillings.

Les lignes de jonction entre plate-formes d'aubes ne sont pas parallèles au vecteur vitesse du flux d'air, ce dernier étant de biais par rapport aux lignes de jonction. Ceci a pour avantage de restreindre les lignes de fuite par rapport à une configuration où le vecteur vitesse du flux d'air est parallèle aux lignes de jonction, comme c'est le cas dans l'état de l'art US 6, 543, 995 B1 , et donc de minimiser les perturbations au niveau aérodynamique.The junction lines between blade platforms are not parallel to the velocity vector of the air flow, the latter being biased relative to the junction lines. This has the advantage of restricting the creepage distances with respect to a configuration where the velocity vector of the air flow is parallel to the connecting lines, as is the case in the state of the art. US 6, 543, 995 B1 , and therefore minimize aerodynamic disturbances.

La présence de plate-formes jointives du côté de la veine aérodynamique permet de réduire la surface de contact entre le flux d'air et la virole extérieure ce qui engendre une réduction de l'érosion de cette dernière.The presence of contiguous platforms on the side of the aerodynamic vein makes it possible to reduce the contact surface between the air flow and the outer shell, which causes a reduction in the erosion of the latter.

De même, la présence de plate-formes jointives assure une bonne étanchéité sans recourir à l'utilisation de matériau élastomère.Similarly, the presence of contiguous platforms ensures a good seal without resorting to the use of elastomeric material.

Les seules ouvertures requises dans la virole extérieure sont celles pour les trous de fixation. Dans le cas d'un assemblage par collage ou co-moulage, la virole extérieure est exempte de toute ouverture.The only openings required in the outer shell are those for the mounting holes. In the case of an assembly by bonding or co-molding, the outer shell is free of any opening.

La suppression des larges ouvertures dans la virole extérieure a pour avantage de ne pas diminuer la résistance structurelle de la virole. Ceci présente plus particulièrement un avantage pour les viroles en composite à fibres longues où les ouvertures dans la virole sectionnent les fibres et diminuent donc particulièrement la résistance mécanique du matériau.The removal of large openings in the outer shell has the advantage of not reducing the structural strength of the shell. This is particularly advantageous for long fiber composite ferrules where the openings in the ferrule sever the fibers and therefore particularly reduce the mechanical strength of the material.

En cas de perte d'aube de soufflante (Fan Blade Out), la suppression des grandes ouvertures et le fait que les plate-formes soient fixées sur la face interne de la virole extérieure permet de confiner l'écrasement des aubes au sein du compresseur basse pression.In case of Fan Blade Out loss, the removal of large openings and the fact that the platforms are fixed on the inner face of the outer shell can confine the crushing of the blades in the compressor. low pressure.

Grâce à ce système d'interface aube/virole extérieure, le montage des aubes est parfaitement interchangeable, c'est-à-dire que la plate-forme et le système de fixation peuvent être identiques tout en ayant des profils ou matériaux d'aubes différents.Thanks to this blade / outer shell interface system, the blade assembly is perfectly interchangeable, that is to say that the platform and the fastening system can be identical while having blade profiles or materials. different.

Le système de fixation étant mécanique, cette solution représente un avantage pour le démontage et remontage des aubes lors d'une réparation, par rapport à une configuration soudée.The fastening system being mechanical, this solution represents an advantage for disassembling and reassembling the blades during a repair, compared to a welded configuration.

Claims (12)

  1. Guide vane stage of a turbine engine comprising a series of fixed blades (2) connecting an inner collar (4) to an outer collar (5), said fixed blades (2) comprising attachment platforms (7) with flat surfaces that co-operate with a plurality of juxtaposed flat facets, said flat facets being located on the inner face of the outer collar (5) in order to ensure attachment with a contact of a flat/flat type between the fixed blades (2) and the outer collar (5), characterized in that said platforms (7) are jointly disposed in order to present a continuous smooth surface to the airflow.
  2. Guide vane stage of a turbine engine according to Claim 1, characterised in that the outer collar (5) is formed by a plurality of juxtaposed flat segments (10).
  3. Guide vane stage of a turbine engine according to any one of the preceding claims, characterised in that the outer collar (5) is made of a composite material.
  4. Guide vane stage of a turbine engine according to any one of the preceding claims, characterised in that the only apertures in the outer collar (5) are those required by the attachment systems for the platforms (7) of the blades (2) on the inner face of the outer collar (5).
  5. Guide vane stage of a turbine engine according to Claim 4, characterised in that the attachment systems comprise a bolted fastener (11).
  6. Guide vane stage of a turbine engine according to Claim 5, characterised in that the bolted fastener (11) has a threaded bolt fixed to the blade (2), said bolt passing through the outer collar (5) so as to be bolted to the outer face of the outer collar by a nut.
  7. Guide vane stage of a turbine engine according to Claim 5, characterised in that the bolted fastener comprises an L-shaped flange (8) integrated into the platform (7) of the blade (2) and in that said flange (8) is bolted to an attachment flange (1) of the outer collars (5).
  8. Guide vane stage of a turbine engine according to Claim 4, characterised in that the attachment systems comprise rivets or "lockbolts" (9).
  9. Guide vane stage of a turbine engine according to Claim 3, characterised in that the platforms (7) of the blades (2) are glued to the flat facets or flat segments (10) of the outer collar (5) made of a composite material.
  10. Guide vane stage of a turbine engine according to Claims 6, 7 or 8, characterised in that the attachment systems are a combination of rivets, bolted fasteners and "lockbolts" (9).
  11. Method for manufacturing a guide vane stage of a turbine engine according to Claim 3 comprising a stage of resin transfer moulding of the outer collar (5).
  12. Method for manufacturing a guide vane stage of a turbine engine according to Claim 3 comprising a cocuring stage by resin transfer for attaching the outer collar to the fixed blades.
EP08172599.6A 2008-12-22 2008-12-22 Assembly of guide vanes Active EP2199544B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP08172599.6A EP2199544B1 (en) 2008-12-22 2008-12-22 Assembly of guide vanes
CA2686988A CA2686988C (en) 2008-12-22 2009-12-03 Guide vane architecture
US12/640,062 US8469662B2 (en) 2008-12-22 2009-12-17 Guide vane architecture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08172599.6A EP2199544B1 (en) 2008-12-22 2008-12-22 Assembly of guide vanes

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EP2199544A1 EP2199544A1 (en) 2010-06-23
EP2199544B1 true EP2199544B1 (en) 2016-03-30

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EP2199544B1 (en) * 2008-12-22 2016-03-30 Techspace Aero S.A. Assembly of guide vanes
EP2211023A1 (en) * 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Guide vane system for a turbomachine with segmented guide vane carrier
EP2696042B1 (en) * 2012-08-09 2015-01-21 MTU Aero Engines GmbH Fluid flow engine with at least one guide blade assembly
EP2930308B1 (en) * 2014-04-11 2021-07-28 Safran Aero Boosters SA Faceted axial turbomachine housing
US10301951B2 (en) 2016-05-20 2019-05-28 United Technologies Corporation Turbine vane gusset
CN112709716A (en) * 2020-12-29 2021-04-27 中国航发沈阳发动机研究所 Compressor stator blade structure
US11828197B2 (en) 2021-12-03 2023-11-28 Rolls-Royce North American Technologies Inc. Outlet guide vane mounting assembly for turbine engines

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US8469662B2 (en) 2013-06-25
CA2686988A1 (en) 2010-06-22
CA2686988C (en) 2016-02-16
US20100158685A1 (en) 2010-06-24
EP2199544A1 (en) 2010-06-23

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